EP0687865B1 - Brûleur pour turbine à gaz à baisse émission de NOx pour montage ultérieur - Google Patents

Brûleur pour turbine à gaz à baisse émission de NOx pour montage ultérieur Download PDF

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Publication number
EP0687865B1
EP0687865B1 EP95304058A EP95304058A EP0687865B1 EP 0687865 B1 EP0687865 B1 EP 0687865B1 EP 95304058 A EP95304058 A EP 95304058A EP 95304058 A EP95304058 A EP 95304058A EP 0687865 B1 EP0687865 B1 EP 0687865B1
Authority
EP
European Patent Office
Prior art keywords
fuel
combustor
nozzle block
passages
flange
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP95304058A
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German (de)
English (en)
Other versions
EP0687865A1 (fr
Inventor
Stephen Eugene Mumford
David Marchant Parker
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens Energy Inc
Original Assignee
Siemens Westinghouse Power Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens Westinghouse Power Corp filed Critical Siemens Westinghouse Power Corp
Publication of EP0687865A1 publication Critical patent/EP0687865A1/fr
Application granted granted Critical
Publication of EP0687865B1 publication Critical patent/EP0687865B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C5/00—Disposition of burners with respect to the combustion chamber or to one another; Mounting of burners in combustion apparatus
    • F23C5/02—Structural details of mounting
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2205/00—Assemblies of two or more burners, irrespective of fuel type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00008—Burner assemblies with diffusion and premix modes, i.e. dual mode burners

Definitions

  • the present invention relates to the combustor section of gas turbine power stations. More specifically, the present invention relates to apparatus for retro-fitting conventional gas turbines to provide for installation of low NOx combustor systems using the existing openings in the turbine cylinder and without significant alteration of the cylinder.
  • the compressor section produces compressed air that is subsequently heated by burning fuel in a combustion section.
  • the hot gas from the combustion section is directed to a turbine section where the hot gas is used to drive a rotor shaft for producing power in a known manner.
  • the combustion section is typically comprised of a shell, or cylinder casing, that forms a chamber for receiving compressed air from the compressor section.
  • a plurality of cylindrical combustors are disposed within the chamber and receive the compressed air, along with the fuel to be burned.
  • a duct is connected to the aft end of each combustor and serves to direct the hot gas from the combustors to the turbine section.
  • turbine systems In order to obviate the pollution problems caused by known conventional turbines and avoid the increased cost and complexity associated with steam injection systems, turbine systems have been developed which include newly designed low NOx combustors. These low NOx combustors provide for reduced pollution levels by operation of the combustors in a premix operation that is known in the art, rather than the diffusion burn operation of conventional turbines. Thus, all of the components necessary for the control of NOx emissions are contained within these new low NOx combustors.
  • low NOx combustors are significantly larger than conventional combustors. Also, these low NOx combustors typically require a pilot nozzle and a two stage main nozzle, thus requiring six fuel supply lines for each combustor, three lines for gas and three lines for liquid fuel. Therefore, as compared to conventional combustor systems, these low NOx combustors systems are significantly larger and comprise more structure that must be installed into the turbine cylinder.
  • new gas turbine power stations can be built with low NOx combustors by designing the new cylinder casing to account for the increased size and complexity of the low NOx combustor apparatus, it is not possible to directly install these larger combustor systems in the relatively small existing aperture of the cylinder casing of conventional turbines. Moreover, it is not feasible to alter the size of the existing cylinder aperture to account for the larger size of the low NOx combustors.
  • the present invention provides a low NOx combustor retro-fit system which satisfies that need.
  • the invention consists in a gas turbine, comprising:
  • Figure 1 is a longitudinal cross-section through a portion of a gas turbine incorporating the low NOx combustor retro-fit system of the present invention.
  • Figure 2 shows a main fuel nozzle block in accordance with the present invention.
  • FIGS. 3a and 3b show a fuel supply adapter in accordance with the present invention.
  • Figure 4 shows a pilot nozzle in accordance with the present invention.
  • FIG. 1 a portion of a longitudinal cross-section of a gas turbine.
  • the gas turbine is comprised of a compressor section 1, a combustor section 2 and a turbine section 3.
  • a rotating shaft 4 extends through the compressor, combustion and turbine sections.
  • the compressor 1 is comprised of alternating rows of rotating blades and stationary vanes that compress ambient air to produce compressed air 6.
  • the combustion section 2 is comprised of a plurality of low NOx combustors 8, each of which is formed by a cylindrical liner as is known in the art.
  • the combustors 8 are circumferentially arranged around the rotor 4 within a chamber 10 formed by a cylinder casing 12.
  • each combustor is joined to a duct 14, commonly referred to as a "transition duct".
  • a duct 14 commonly referred to as a "transition duct”.
  • a portion of the compressed air 6 enters each of the combustors 8 at its front end along with a supply of fuel, preferably oil and/or natural gas, the fuel being supplied in the manner described in detail below.
  • the fuel is introduced into a combustion zone enclosed by each of the combustors 8, via fuel nozzles, as also described in detail below. In the combustion zone, the fuel is burned in the compressed air to produce a flow of hot gas 16.
  • the hot gas 16 is directed to the turbine section 3, as the hot gas is expanded by duct 14.
  • the front end of a low NOx combustor 8 is excessively large such that it cannot be directly mounted to the cylinder casing 12 at the existing aperture 18 that has previously been used for the direct mounting of smaller conventional combustors. Since the mounting flange 20 at the front end of the low NOx combustor cannot be flushly mounted against the wall of the cylinder casing over aperture 18, the present invention provides a retro-fit system that provides for installation of the low NOx combustors in the existing aperture 18 of the cylinder casing.
  • a retro-fit system in accordance with the present invention provides that low NOx combustors can be directly mounted to the existing transition ducts 14 and no significant alteration of the turbine apparatus and cylinder casing is necessary.
  • Low NOx combustors 8 are mounted to main fuel nozzle block 22.
  • a preferred embodiment of nozzle block 22 is shown in detail in Fig. 2. Referring to Figs. 1 and 2, the mounting flange 20 of combustors 8 is bolted to the flange 24 of the nozzle block 22. Accordingly, the main fuel nozzles 28 which project from the aft end 26 of the nozzle block extend into the low NOx combustors for spraying fuel into the combustors in a known manner.
  • the front end 30 of the main fuel nozzle block 22 is sized to fit over aperture 18 such that the nozzle block is mounted to the cylinder casing 12 by bolts 32 which extend through the cylinder casing and into the front end 30 of the nozzle block. Thus, a large portion of the aft end 30 of the nozzle block 22 is in communication with aperture 18.
  • the flanged front end of conventional combustors have previously been directly mounted to the cylinder casing using only four such bolts 32, with the bolts being evenly spaced around the circumference of the circular aperture 18.
  • the nozzle block 22 has four annular fuel passages 34, 36, 38, 40 for receiving a supply of fuel.
  • fuel passages 34 and 36 receive a supply of liquid fuel
  • fuel passages 38 and 40 are supplied with gas in the manner described below.
  • the nozzles 28 are alternatingly connected into flow communication with the fuel passages such that one nozzle is connected to liquid fuel passage 34 and gas fuel passage 38, via channels 42 and 44 respectively, while an adjacent nozzle is connected to liquid fuel passage 36 and gas fuel passage 40, via channels similar to those shown and labeled as 46 and 48 respectively.
  • Flexible bellows 56 in the connection of the nozzles on the aft end 26 of the nozzle block provide leak free connections and minimize differential thermal expansion stresses in the nozzles.
  • a fuel supply adapter 60 for supplying fuel to the main nozzle block 22, and thus the combustors 8, in accordance with a preferred embodiment of the present invention is shown in Figs. 3a and 3b.
  • Gas fuel supply pipes 62, 64 are mounted in manifold 66 such that when manifold 66 is mechanically connected to the front end 30 of nozzle block 22, the gas fuel supply pipes 62, 64 are in flow communication with annular passages 38, 40 respectively.
  • Flanges 68, 70 are hooked up to separate gas fuel supply manifolds in a known manner such that gas is supplied to pipes 62, 64 and delivered to nozzles 28, via nozzle block 22 in the manner described above.
  • liquid fuel supply pipes 72, 74 are mounted in manifold 66 and connected separately, via pipe connections 75, to oil supply manifolds in a known manner for supplying liquid fuel to the annular passages 34, 36 respectively, and thus nozzles 28, in the described manner.
  • the present invention is not intended to be limited to the arrangement of the fuel supply pipes shown in Figs. 3a and 3b. Moreover, the present invention is not intended to be limited to a system for supplying both gas and liquid fuel and the system can operate in accordance with the present invention with either liquid or gas fuel exclusively.
  • manifold 66 is disposed in the aperture 18 of casing 12 and is bolted to the front end 30 of the nozzle block by bolts 76. Accordingly, the fuel supply pipes 62, 64 and 72, 74 extend out through aperture 18 to the outside of the cylinder casing.
  • a pilot nozzle 80 in accordance with the present invention is shown. As shown in Figs. 1, 2 and 3a-b, the pilot nozzle extends through the central aperture 82 in the manifold 66 of the fuel supply adapter 60, and further through the central bore 84 in the main fuel nozzle block 22 such that the pilot nozzle extends into the combustor for spraying fuel therein a known manner.
  • Flange 86 located near the center of the pilot nozzle 80 is mechanically connected to the front end of the manifold 66 by bolts 88 for securing the pilot nozzle apparatus.
  • Gas is supplied to the pilot nozzle through chamber 90, while liquid fuel is supplied through pipe 92, the fuel supplies for the pilot nozzle being located outside of the cylinder casing.
  • the pilot nozzle sprays fuel into the low NOx combustors for creating a pilot flame therein in a known manner.
  • low NOx combustors can be mounted to the cylinder casing 12 and to the transition duct 14, and the necessary fuel supply apparatus can be accommodated within the existing aperture 18 in the casing, without any significant alteration of the conventional gas turbine apparatus.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Claims (9)

  1. Turbine à gaz, comportant:
    un compresseur (1) pour fournir de l'air comprimé (6);
    un carter de cylindre (12) pour recevoir ledit air comprimé provenant dudit compresseur, ledit carter de cylindre ayant un orifice (18) comportant un premier diamètre;
    un appareil de combustion (8) susceptible de brûler un carburant dans ledit air comprimé, ledit appareil de combustion situé dans ledit carter de cylindre et ayant une bride d'appareil de combustion (20), ladite bride d'appareil de combustion ayant un diamètre de bride d'appareil de combustion essentiellement supérieur audit premier diamètre;
    un bloc à gicleurs (22) ayant une première extrémité (30) et une deuxième extrémité (26), ledit bloc à gicleurs (22) ayant une pluralité de gicleurs de carburant (28) pour pulvériser ledit carburant dans ledit appareil de combustion, ledit bloc à gicleurs ayant une bride de bloc à gicleurs (24), ladite bride de bloc à gicleurs (24) ayant un diamètre de bride de bloc à gicleurs essentiellement de la même dimension que ledit diamètre de bride d'appareil de combustion, caractérisé en ce que ladite bride de bloc à gicleurs (24) est en liaison mécanique avec ladite bride d'appareil de combustion (20) de facon telle que lesdits gicleurs (28) s'allongent jusqu'à l'intérieur dudit appareil de combustion (8), ladite première extrémité (30) étant en liaison mécanique avec ledit carter de cylindre (12) sur ledit orifice (18).
  2. Turbine à gaz selon la revendication 1, ledit bloc à gicleurs comportant en outre une pluralité de conduits à carburant (34, 36, 38,40) en communication d'écoulement avec un apport dudit carburant, à partir duquel ledit carburant est amené auxdits gicleurs par l'intermédiaire desdits conduits à carburant.
  3. Turbine à gaz selon la revendication 2, comportant en outre des moyens d'apport de carburant pour amener ledit carburant auxdits conduits à carburant.
  4. Turbine à gaz selon la revendication 3, dont ledit moyen d'apport de carburant est en liaison mécanique avec ladite première extrémité.
  5. Turbine à gaz selon la revendication 1, caractérisée en outre par:
    un adaptateur d'apport de carburant (60) ayant une plura!ité de conduits de distributeur, ledits conduits de distributeur en communication d'écoulement avec un apport dudit carburant, ledit adaptateur d'apport de carburant fixé de manière mécanique audit bloc à gicleurs de façon telle que chacun des conduits de distributeur est en communication d'écoulement avec une unité correspondante desdits conduits à carburant;
    un gicleur pilote (80) en communication d'écoulement avec un apport dudit carburant, ledit gicleur pilote s'allongeant au travers d'un orifice de gicleur pilote et dans ledit appareil de combustion pour pulvériser le carburant dans ledit appareil de combustion; et
    un élément de turbine (3) pour la dilatation dudit gaz chaud.
  6. La turbine à gaz selon la revendication 5, ledit adaptateur d'apport de carburant ayant une pluralité de tubulures d'apport de carburant (62, 64, 72, 74) dont le nombre correspond à celui de ladite pluralité de conduits de distributeur, chacun de ladite pluralité de tubulures d'apport de carburant en communication d'écoulement avec un élément correspondant de ladite pluralité de conduits de distributeur.
  7. La turbine à gaz selon la revendication 6, ledit adaptateur d'apport de carburant ayant quatre conduits de distributeur.
  8. La turbine à gaz selon la revendication 7, dont deux desdits conduits de distributeur reçoivent le gaz carburant et les deux autres desdits conduits de distributeur reçoivent le carburant pétrolier liquide.
  9. La turbine à gaz selon la revendication 5, dont ledit adaptateur d'apport de carburant comporte des premier, deuxième, troisième et quatrième conduits de distributeur, lesdits premier et troisième conduits en communication d'écoulement avec un apport de gaz carburant et lesdits deuxième et quatrième conduits de distributeur en communication d'écoulement avec un apport de carburant liquide pétrolier, l'un desdits gicleurs à carburant en communication d'écoulement avec lesdits premier et deuxième conduits de distributeur et une unité adjacente desdits gicleurs en communication d'écoulement avec ledit troisième et quatrième conduits de distributeur.
EP95304058A 1994-06-13 1995-06-13 Brûleur pour turbine à gaz à baisse émission de NOx pour montage ultérieur Expired - Lifetime EP0687865B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US08/259,106 US5415000A (en) 1994-06-13 1994-06-13 Low NOx combustor retro-fit system for gas turbines
US259106 2002-09-27

Publications (2)

Publication Number Publication Date
EP0687865A1 EP0687865A1 (fr) 1995-12-20
EP0687865B1 true EP0687865B1 (fr) 1999-09-22

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EP95304058A Expired - Lifetime EP0687865B1 (fr) 1994-06-13 1995-06-13 Brûleur pour turbine à gaz à baisse émission de NOx pour montage ultérieur

Country Status (7)

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US (1) US5415000A (fr)
EP (1) EP0687865B1 (fr)
JP (1) JP3856158B2 (fr)
KR (1) KR100354306B1 (fr)
CA (1) CA2151559A1 (fr)
DE (1) DE69512316T2 (fr)
TW (1) TW360331U (fr)

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Also Published As

Publication number Publication date
CA2151559A1 (fr) 1995-12-14
JP3856158B2 (ja) 2006-12-13
US5415000A (en) 1995-05-16
DE69512316T2 (de) 2000-03-30
KR100354306B1 (ko) 2002-12-28
JPH085075A (ja) 1996-01-12
EP0687865A1 (fr) 1995-12-20
TW360331U (en) 1999-06-01
DE69512316D1 (de) 1999-10-28
KR960001440A (ko) 1996-01-25

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